DE102010010508B4 - Unmanned aerial vehicle with a payload space - Google Patents

Abstract

An unmanned aerial vehicle (2) having a) a payload space (6) closed to the outside with a hatch (8, 10, 34), the hatch (10, 34) opening downwardly so that payload elements are downwardly out of the payload space (6) are ejectable, and b) in the payload space (6) arranged payload container (20, 22, 58, 66), wherein - the payload container (20, 22, 58, 66) a rotatably mounted turret spindle (24, 42, 68 ) having a number of turret locations (46) and a drive (70) for rotating the turret spindle (24, 42, 68) relative to the fuselage (56) of the aircraft (2), wherein turrets are disposed on the turret spindle for deployment during a flight - the payload container (20, 22, 58, 66) forms an outer skin region of the aircraft (2) and - the hatch (10, 34) is part of the payload container (20, 22, 58, 66) and the payload container (20, 22, 58, 66) in a receptacle (12) of the payload space (6) can be locked.

Description

The invention relates to an unmanned aircraft with a payload space, which is closed to the outside with a hatch.

To combat air or ground targets from the air, it is known to attach guided missiles from below to an aircraft, for example under the wings, and drop them during the flight before their engine ignites and they move towards their destination. In order to reduce burdens and risks for pilots and air personnel, unmanned aerial vehicles are increasingly being used for carrying and dropping missiles.

From the US 5 067 411 A is a weapon system is known in which a primary weapon is equipped with ejectable secondary weapons, which are arranged in recesses in the primary weapon. The DE 10 2005 042 484 A1 discloses an unmanned gliding missile in which a bomb is arranged from below at a longitudinal structure of the gliding missile connecting the bow and stern sections. The DE 36 01 095 C1 shows a flying dispenser, from which submunition can be ejected by means of an energy source. The FR 2 640 372 A1 deals with the spreading of ammunition over powered projectiles or containers. In order for the ammunition can leave the bullet, the blowing of the shell of the same is provided.

From the DE 34 21 167 A1 and the DE 24 13 983 A1 weapons are known in which a drum magazine for picking up ammunition is used.

It is an object of the present invention to provide a safe unmanned aerial vehicle for carrying and launching missiles.

This object is achieved by an unmanned aerial vehicle according to the features of claim 1.

The invention is based on the consideration that it is advantageous for better camouflage of aircraft not to engage the missiles on the outside of the aircraft, but to store them inside the aircraft in a closed container, for example in a weapons bay. Irregular outer contours of the aircraft are avoided, so that it is harder to detect by a radar. By allowing the hatch to open downwardly, the payload elements may drop out of the aircraft at the bottom and, for example, launch their engine and move away from the unmanned aerial vehicle.

An unmanned aerial vehicle may be understood to mean an aircraft without a control room for a pilot who is flying. It is expediently prepared for control solely by remote control, so that it can be directed from, for example, a ground station during its entire flight. The unmanned aerial vehicle is expediently a barrelable aircraft. This is hereinafter understood to mean an aircraft whose payload space has at least one volume of a barrel, ie 159 liters and which is designed to carry at least 159 kg payload or is prepared in accordance with the regulations. The hatch is expediently part of the outer skin of the aircraft and it is movable to open the payload space to the outside. The downward direction refers to the direction of gravity, with an unmanned aerial vehicle standing on a horizontal plane.

According to the invention, a turret spindle with a number of turret locations is arranged in the payload space. At each turret location, for example, a payload element, such as a guided missile, can be arranged so that by rotating the turret spindle first a turret location is located at the lowest point within the payload space and this payload element can be dropped, then another turret slot to the deepest Position, by further turning another turret, etc., so that each payload element can be ejected from the deepest place within the payload space.

To rotate the turret spindle, a drive is provided which is prepared for rotation of the turret spindle relative to the fuselage of the aircraft, in particular about an at least substantially horizontal axis. The drive may be part of the turret spindle or part of a payload container in which the turret spindle can be arranged. For controlling the rotation, the aircraft suitably comprises a control means which is prepared to rotate a predetermined turret position to a lowest position on the hatch. The control means is expediently an electronic data processing system with a corresponding control program.

The turret positions on the turret spindle are advantageously designed differently, so that different payload elements can be attached to the turret spindle. The control means is suitably prepared to select a payload element according to predetermined parameters and to rotate to the lowest point or to the hatch so that it can be ejected from the aircraft. Further, it is advantageous if at least one of the turret places with at least two grippers is equipped for grasping a hull of a missile. It can be dispensed with holding elements on the missile, so that the construction and the missile itself is facilitated. The grippers can be designed for pincer-like gripping of the missile, wherein they are adjustable in particular in their distance from one another, so that they can engage at different positions of the missile.

For quick and easy loading of the payload space with a load, it is advantageous if the aircraft is equipped with a receptacle for the loading, which is advantageously carried out self-closing. The receptacle is expediently prepared for tool-free locking of the load in the payload area. The loading may be the turret spindle, which is conveniently equipped with a number of payload elements, or a payload container containing therein payload elements, such as the turret spindle or other object. Conveniently, the receptacle is prepared for automatically locking the load when loading the load into the payload space. Thus, the recording does not have to be manually operated within the aircraft, but the aircraft can be completely loaded from the outside. The automatic locking can be done by latching upon insertion of the load into the payload space or by a pickup drive that can be set in motion by an insertion movement of the load into the payload space or a control signal from an operator.

A further advantageous embodiment of the invention provides that the unmanned aerial vehicle has a loading device with an opening in the outer skin of the aircraft upwards for loading the payload space from above. Especially with smaller unmanned aerial vehicles there is little space between the aircraft and the ground, so that loading from above accelerates and facilitates the loading process. The loading device may have a hatch for opening the payload space upwards, through which the payload space can be opened and closed upwards.

According to the invention, the unmanned aerial vehicle carries a payload container arranged in the payload space. Under a payload container can be understood after at least 4 of 6 pages closed container, which is introduced during a loading process as part of a payload in the payload space. The payload container and the aircraft are suitably coordinated with each other in terms of their geometry and a receptacle for locking the payload container in the payload space.

Unmanned aerial vehicles prepared for high-performance flight must have high stability in order to cope with the high mechanical loads at high airspeeds and / or fast flight maneuvers. A large opening in the outer skin of the aircraft for receiving payload elements, such as the turret spindle or the payload container, significantly affects the stability of the aircraft. In order to regain at least a portion of the lost stability through the opening, it is advantageous if the payload container is locked in the fuselage of the aircraft such that it forms an element that contributes to the rigidity of the fuselage.

The payload container forms an area of the outer skin of the aircraft. In this way, payload elements in the payload container can be introduced into the aircraft and locked there without being shielded from the outside by both the cargo canister and another outer skin of the aircraft. It can be saved weight and space. The hatch is part of the payload container so that the payload elements can be dropped after opening the payload container.

Conveniently, the payload container is locked in the fuselage so that it torsionsversteift the torso, so the hull with the locked Nutlastbehälter is more stable against twisting in, as without the locked payload container. The payload container may be equipped with a plurality of brackets over which it is braced with the fuselage. The stress may be a compressive stress or a tensile stress. The brackets can form the receptacle or a part of it. Advantageously, the payload container closes an opening of the fuselage. In particular, he is locked on at least four brackets with the hull braced so that it counteracts a distortion of the opening. Warping may be, for example, a diamond formation of a rectangular opening. Advantageously, the brackets are arranged on the periphery of its outer skin-forming surface, with a distance of up to 20 cm from the periphery being permissible.

To stiffen the aircraft, it is advantageous if the payload container is provided with diagonal struts, which counteract a twisting of the payload container. The diagonal struts can be arranged in the interior of the payload container and they are advantageously integrally connected to the payload container, for example, welded. They are advantageously an integral part of the payload container.

In the payload container, a turret spindle is rotatably mounted or others Payload elements. Advantageously, the drive for rotating the turret spindle is an integral part of the payload container. The payload container may include a receptacle for receiving and locking the turret spindle in the payload container as described above.

Further, it is advantageous if the payload container missile for discharge during a flight and at least one auxiliary unit to support a readiness of operation of the missile includes. An auxiliary unit may be a unit for cooling the missile or a part thereof, a battery charger, electronic means for monitoring or diagnosing an element of the missile, or for controlling an element of the missile or for transmitting data to the missile, for example for instructing a seeker head to a predetermined one Aim.

The invention also relates to a method for loading an unmanned aerial vehicle. An aircraft that can be opened with a hatch down so that payload elements can be ejected downwardly from the payload space is provided with a large opening that reduces the stability of the aircraft. It is therefore advantageous to load the aircraft from below, since a load from above creates an additional opening impairing the stability of the aircraft. Below an aircraft, however, there is often little space available for rapid and accident-free loading.

To solve this problem, it is proposed that the load is placed on a support base according to the invention, for example on a building floor or the ground, the aircraft is lowered from above onto the load and thereby the load is introduced into a payload space of the aircraft. Loading from below can be made easier and safer. Since unmanned aircraft usually have holding elements for lifting, for example, to be parked with a crane, a lowering of the aircraft on the load is associated with no great effort. The aircraft can be loaded quickly and safely with no additional opening up, so it retains high rigidity for good flight performance.

In an advantageous embodiment of this invention, the load is automatically locked upon reaching a predetermined position in the payload space. The automatic locking can be achieved by reaching the predetermined position or by an operator input, for. B. by pressing a button on the aircraft to be triggered.

Advantageous embodiments of the invention are explained in the following description of the drawings. The drawing and the description contain numerous features in combination, which the skilled person expediently consider individually and will summarize meaningful further combinations.

Show it

1 An unmanned aerial vehicle with an overhead and a downhole hatch and an indicated payload space,

2 two payload containers with two different revolver spindles, each carrying a guided missile,

3 a turret equipped with two grippers that hold a guided missile,

4 a representation of an anchorage of a payload container in the hull of the unmanned aerial vehicle,

5 the payload container with several brackets for anchoring in the fuselage of the aircraft,

6 a schematic sectional view of four of the brackets and

7 two payload containers arranged lengthwise one behind the other, each with a turret spindle carrying a plurality of guided missiles

1 shows an unmanned aerial vehicle 2 with a length of about 8 m and a payload of about 300 kg. The aircraft 2 is with a control means 4 equipped in the form of an electronic data processing system, which is via a transmitter and receiver, not shown, with a ground station in a data exchange. About this data exchange is the aircraft 2 controlled by a pilot in the ground station, allowing the aircraft 2 remotely controlled his mission. A control room for a flying pilot is in the aircraft 2 unavailable.

Inside the aircraft 2 is however a payload space 6 arranged in 1 indicated by dashed lines. The payload space 6 with a volume of over 1 m ³ is from above through a first hatch 8th and from below through a second hatch 10 accessible. Alternatively, only the hatch 10 available and instead of the hatch 8th is the hull 56 of the aircraft 2 in the place of the hatch 8th closed to a higher stiffness of the fuselage 56 to reach. The two hatches 8th . 10 each include two hatch covers, which are in the manner of a double-wing door up against each other and are zuklappbar, so the payload space 6 can be opened up and down. Each opening forms with its hatch 8th . 10 a loading device for loading the aircraft 2 from above or below.

For loading the aircraft 2 with a load 18 ( 2 ) there are two options available. So in a first way the upper hatch 8th opened and the loading 18 from above into the payload space 6 be introduced. In a second possibility, the hatch 10 opened and the loading 18 from below into the payload space 6 introduced. However, because of the small size of the aircraft 2 under this only a flat space is available, and there the aircraft 2 is relatively easy, this is provided with not shown holding elements for lifting by, for example, a crane. That way the loading can be done 18 on a ground, for example, a runway, be parked and the aircraft 2 is with hatch open 10 from the top of the load 18 lowered, which is conveniently already positioned at such a height that they lower the aircraft 2 completely off the payload space 6 is recorded.

The loading can be in one shot 12 , in the 5 based on twelve brackets 14 and counterholds 16 is indicated, introduced and there for example by snapping and / or a motor drive for bracing the brackets 14 and counterholds 16 against each other, be locked. Every holder 14 forms with a counter bracket 16 a self-closing closure, which automatically locks the load 18 when loading the load 18 in the payload space 6 is prepared.

For devaluating payload elements of the load 18 during the flight of the aircraft 2 can the lower hatch 10 be opened and the payload elements are out of the hatch 10 actively thrown down or they fall out of the hatch 10 down out.

Possible loads 18 such as two payload containers 20 . 22 , are in 2 outlined. The payload containers 20 . 22 can each individually as a single load 18 in the payload space 6 are introduced and locked there or together form a single load 18 ,

The cuboid payload container 20 carries inside it a revolver spindle 24 using an unillustrated drive around an axis of rotation 26 inside the payload container 20 is rotatably mounted. The turret spindle 24 has eight turret seats 46 in which four large and four small steering missiles 28 . 30 , are locked. Due to the rotatability of the turret spindle 24 every turret can 46 to the lowest position 32 in the immediate vicinity of a hatch 34 of the payload container 20 be positioned so that the corresponding missile 28 at a release from the turret 46 down from the hatch 34 falls out or is actively thrown out. The hatch 34 is with two flaps 36 hinged in the manner of a double-wing door 38 up against each other and are zuklappbar. The hatch 34 can the hatch 10 of the aircraft 2 replace the hatch 10 at in the payload space 6 used and locked payload container 20 through the hatch 34 is replaced and is superfluous.

Next is the container 20 with auxiliary equipment 40 in support of the operational readiness of the guided missiles 28 . 30 provided, z. B. for charging of on-board batteries of the missile 28 . 30 , for data supply with target data, for data query of analysis data on the condition of the guided missile 28 . 30 or similar. Alternatively, some or all of the auxiliary equipment 40 inside the turret spindles 24 . 42 be arranged rotatable, so they always positioned the same to the missiles 28 . 30 are.

The payload container 22 is a container identical to the payload container 20 executed, however, is with another turret spindle 42 loaded and he carries other auxiliary equipment 40 , which - analogous to the payload container 20 - integral part of the payload container 22 are. The turret spindle 42 is provided with four spindle positions, each with several grippers 44 wear.

Such a revolver place 46 is in 3 shown in more detail. On a backbone 48 , which is part of the turret spindle 42 is, are two grippers 44 slidably fastened in the way that their distance 50 is infinitely adjustable to each other. Here are the grippers 44 on the backbone 48 Lockable in any position. Every grapple 44 is with two mutually movable arms 52 equipped with a motor 54 in the manner of a pair of pliers can be moved to and. In 3 are the two grippers 44 only for the sake of better understanding in two positions, namely the backbone 48 in open position and also on the backbone 48 - Although this is not shown for the sake of clarity - the guided missile 28 holding tight, holding it at the revolver place 46 is held clamped.

To load the turret 46 with a guided missile 48 can the turret place 46 all the way down to the hatch 34 be rotated. The guided missile 28 is used from below and the arms 52 be closed by a motor, so that they are the missile 28 at a Place of his cylindrical trunk 56 hold clamped. Subsequently, the turret spindle 42 be rotated, so a next revolver place 46 down and near the hatch 34 is arranged so that a next missile 28 between the arms 52 the gripper 44 In an alternative loading method is the turret spindle 42 initially outside the payload container 22 and will with guided missiles 28 loaded. The fully assembled turret spindle 42 is then in the payload container 22 introduced and there in a receptacle of the payload container 22 locked. In both load variants, the fully loaded payload container 22 then in the payload space 6 of the aircraft 2 introduced and there in the recording 12 locked.

4 shows another Nutzlastbehalter 58 , analogous to the payload container 20 The following description is essentially limited to the differences between the individual exemplary embodiments in the 2 to 7 , reference being made always to the respective preceding embodiments with respect to features and functions that remain the same. Substantially identical components are always numbered with the same reference numerals and features not mentioned are taken over in the respective following exemplary embodiments, without being described again The payload container 58 is with four diagonal braces 60 provided parallel to long edges 62 of the payload container 58 run and reinforce this. As a result, the payload container 58 torsionally stiffened, with the diagonal struts 60 Counteract a twisting. The payload container 58 is so in the payload space 6 that he is part of the outer skin 64 of the aircraft 2 forms. The hatch 34 is made slightly smaller than in the embodiment 2 to the torsional stiffness of the payload container 58 minimize as little as possible.

For locking the payload container 58 in the utility room 6 and with the outer skin 64 of the aircraft 2 he is with twelve brackets 14 provided in 5 indicated schematically are adjacent to each holder 14 is each a counter-holder 16 as a bracket of the aircraft 2 positioned, with the upper counter supports 16 at completely in the payload range 6 inserted payload container 58 over the brackets 14 and the lower mounts 16 side of the brackets 14 are positioned.

When inserting the payload container 58 in the payload space 6 become the six upper mounts 14 from below into the overlying mounts 16 partially inserted and latched in the counter supports 16 Any brackets 14 forms so with their counterhold 16 each a self-closing closure, the case of insertion of the payload container 58 in the payload space 6 locked by latching automatic The counter supports 16 In addition, each may be provided with a motor drive, the holders 14 even further in the Gegenhalterungen 16 retract and - in addition to locking - continue to lock

After contacting the upper brackets 14 with the corresponding countermounts 16 grab the lower mounts 16 with the help of a motor drive in the lower brackets 14 of the payload container 58 and pull the brackets 16 each to himself. This also automatic closures are formed. This will be the bottom of the payload container 58 stuck to the hull 56 , especially with the outer skin 64 of the aircraft 2 , tense, leaving the hull 56 contracted and the payload container 58 is pulled apart the payload container 58 is also braced in the vertical direction by a force effect between the upper Gegenhalterungen 16 and the lower mounts 16 , In this way is the payload container 58 at least two-dimensional, in particular three-dimensional in the aircraft 2 braced and can - by its own torsional stiffness - the torsional stiffness of the aircraft 2 increase overall.

Another example of the tension of the payload container 58 in the hull 56 of the aircraft 2 is in 6 shown the picture 12 is only schematically using four brackets 14 or counter-holders 16 indicated, it being apparent that the underside of the Nutzlastbehalters 58 Part of the outer skin 64 of the aircraft 2 forms. In this embodiment, the upper brackets 14 laterally braced with a small component upwards, so that the payload container 58 pulled outward and the hull 56 inside to the payload container 58 is pulled.

7 shows two payload containers 66 , which are coupled together and lengthwise one behind the other in the payload space 6 are arranged. In every payload container 66 is in each case a turret spindle 68 locked and mechanically with a drive 70 connected to the rotation of the relevant turret spindle 68 is prepared, controlled by the control means 4 , Inside each revolver spindle 68 are each auxiliary units for the supply and / or monitoring of missiles 28 co-rotating arranged. A rotatable interface connects to the respective payload container 66 and from there to the control means 4 produced. Also the drive 70 may in an alternative embodiment within the turret spindle 68 be arranged, mechanically in Nutzlastbehalter 66 supported.

In an alternative embodiment, the turret spindle 24 . 42 without a payload container 20 . 22 in the payload space 6 of the aircraft 2 introduced and in a reception of the payload space 6 locked, analogous to the recording 12 can be executed. Also in this embodiment closures are expediently each with at least one holder 12 and a counter-holder 16 present, which is the turret spindle 24 . 42 lock automatically during or after insertion. To play a game between recording and turret spindle 24 . 42 To avoid tampering the fasteners turret spindle 24 . 42 in the payload space 6 , z. B. as described above.

All or individual characteristics of the payload container 20 . 22 . 58 . 66 can also be in a different payload container 20 . 22 . 58 . 66 be realized. This also applies to the different turret spindles 24 . 42 . 68 ,

LIST OF REFERENCE NUMBERS

2

aircraft

4

control means

6

payload space

8th

hatch

10

hatch

12

admission

14

bracket

16

against mount

18

loading

20

payload container

22

payload container

24

turret spindle

26

axis of rotation

28

Missile

30

Missile

32

position

34

hatch

36

flap

38

hinge

40

auxiliary power unit

42

turret spindle

44

grab

46

turret location

48

backbone

50

distance

52

poor

54

engine

56

hull

58

payload container

60

diagonal strut

62

longitudinal edge

64

shell

66

payload container

68

turret spindle

70

drive

Claims (7)

Unmanned aerial vehicle ( 2 ) with a) a payload space ( 6 ), which faces outward with a hatch ( 8th . 10 . 34 ) is closed, the hatch ( 10 . 34 ) opens downwards so that payload elements down from the payload space ( 6 ) and b) one in the payload space ( 6 ) arranged payload container ( 20 . 22 . 58 . 66 ), wherein - the payload container ( 20 . 22 . 58 . 66 ) a rotatably mounted turret spindle ( 24 . 42 . 68 ) with a number of turret locations ( 46 ) and a drive ( 70 ) for rotation of the turret spindle ( 24 . 42 . 68 ) relative to the fuselage ( 56 ) of the aircraft ( 2 ), wherein on the turret spindle missiles are arranged for discharge during a flight, - the payload container ( 20 . 22 . 58 . 66 ) an outer skin area of the aircraft ( 2 ) and - the hatch ( 10 . 34 ) Part of the payload container ( 20 . 22 . 58 . 66 ) and the payload container ( 20 . 22 . 58 . 66 ) in a recording ( 12 ) of the payload space ( 6 ) is lockable. Unmanned aerial vehicle ( 2 ) according to claim 1 with a control means ( 4 ) for controlling the rotation of the turret spindle ( 24 . 42 . 68 ), so that a predetermined turret position ( 46 ) to a lowest position and to the hatch ( 10 . 34 ) is rotated. Unmanned aerial vehicle ( 2 ) according to one of the preceding claims with the inclusion ( 12 ) for the payload container ( 20 . 22 . 58 . 66 ) with a self-closing closure, which is used to automatically lock the payload container ( 20 . 22 . 58 . 66 ) when loading the payload container ( 20 . 22 . 58 . 66 ) in the payload space ( 6 ) is prepared. Unmanned aerial vehicle ( 2 ) according to one of the preceding claims with a loading device having an opening in the outer skin of the aircraft ( 2 ) up to load the payload space ( 6 ) from above. Unmanned aerial vehicle ( 2 ) according to one of the preceding claims, wherein the payload container ( 20 . 22 . 58 . 66 ) in the payload space ( 6 ) is locked in such a way that it forms an element that contributes to the rigidity of the fuselage ( 56 ) of the aircraft ( 2 ) contributes. Unmanned aerial vehicle ( 2 ) according to one of the preceding claims, wherein the payload container ( 58 ) with diagonal braces ( 60 ), a twisting of the payload container ( 58 ) counteract. Unmanned aerial vehicle ( 2 ) according to any one of the preceding claims, wherein in Payload container ( 20 . 22 . 58 . 66 ) at least one auxiliary unit ( 40 ) in support of operational readiness of missiles ( 28 . 30 ) is arranged.

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